Rotating Detonation Combustion for Space Engines using Reduced Toxicity Hypergolic Propellants

The Purdue/INSpace LLC team seeks to advance propulsion technology for space engines using storable propellants via the use of rotating detonation combustion. By incorporating an annular combustion chamber with the proper injector design, hydrodynamic instabilities are amplified and create detonation waves that traverse the circumference of the combustor at speeds in excess of 2 km/s. This rapid combustion not only reduces combustor volume by an order of magnitude, but also offers the potential to substantially increase engine specific impulse. Thrust gains come from the ability to detonate propellants and sustain combustion at higher pressures than in conventional engines. Moreover, the use of miscible liquids allows for the potential to detonate well-mixed liquids whose detonation pressures exceed those of gaseous systems by several orders of magnitude. By using less toxic fuels and rotating detonation combustion, more affordable, higher performing space engines can be realized.

This project explores higher specific impulse and lower weight space engines for a variety of NASA missions including Orbital Maneuvering/Reaction Control Systems, Planetary Descent/Ascent, Deep Space Exploration. An additional benefit from this project will be reduced operations costs using lower toxicity fuels

This is early/mid-stage (TRL 4) — the most realistic path in is NASA SBIR/STTR, which funds small businesses and research institutions to develop technology aligned with NASA's needs (equity-free, phased funding). Check whether a current SBIR/STTR solicitation topic overlaps with this project's technology area, or contact the project directly (above) to ask.

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